apollo service module interior

The forward compartment was separated from the central by a bulkhead and was divided into four 90-degree wedges.

The ECS radiators were located on the aft section of Sectors 2 and 5. (Star Trek: First Contact; Star Trek: Enterprise opening credits, ENT: "First Flight"), Commodore Maxwell Forrest had a model of the Apollo Command/Service Module in his office at Starfleet Command in 2143. The fairing externally contained a retractable forward-facing spotlight; an EVA floodlight to aid the Command Module pilot in SIM film retrieval; and a flashing rendezvous beacon visible from 54 nautical miles (100 km) away as a navigation aid for rendezvous with the Lunar Module (LM).

The Block II aft heat shield was a rectangular shape with slightly rounded corners at the propellant tank sectors. After the last mission on Luna, the spacecraft was responsible for transporting astronauts to the space station Skylab. The Service Module was cast off and allowed to burn up in the atmosphere before the Command Module re-entered and brought the crew home. Block II incorporated a revised CM heat shield design, which was tested on the unmanned Apollo 4 and Apollo 6 flights, so the first all-up Block II spacecraft flew on the first manned mission, Apollo 7. The CSM was initially designed to return all three astronauts from the lunar surface on a direct-descent mission which would not use a separate Lunar Module, and thus had no provisions for docking with another spacecraft. from Apollo Training Manual "Apollo Spacecraft & Systems Familiarization" (March 13, 1968) Command and Service Module Engine Locations. This was an array of four 31-inch (0.79 m) diameter reflectors surrounding a single 11-inch (0.28 m) square reflector. Schematics of the Apollo Command Module interior and the Lunar Module were scanned by the Talosians as they reviewed the library computer files of the USS Enterprise in 2254. Excess movement in the vehicles during the 'hard dock' process could cause damage to the docking ring and put stress on the upper tunnel.

After CSM separation from the SLA, it deployed at a right angle to the SM. By January 1964, North American started presenting Block II design details to NASA. The Unified Crew Hatch (UCH) measured 29 inches (74 cm) high, 34 inches (86 cm) wide, and weighed 225 pounds (102 kg). On the flight of Apollo 13, the EPS was disabled by an explosive rupture of one oxygen tank, which punctured the second tank and led to the loss of all oxygen. They were pressurized by 1.1 pounds (0.50 kg) of helium stored at 4,150 pounds per square inch (28.6 MPa) in two tanks. (TNG: "Future Imperfect"). At jettison, the CM umbillical connections were cut using a pyrotechnic-activated guillotine assembly. The SM Model is a preliminary model with few, but accurate external hull features …

various tests including acoustic vibration and drop tests, and water egress training. It was arranged into three panels, each emphasizing the duties of each crew member. More Vintage Space.

diameter (27 cm) and was directly over the center couch. The Apollo spacecraft was a type of 20th century Earth spacecraft used by the United States of America during the 1960s and 1970s. The central heat shield consisted of 40 individual panels interspersed with several holes and openings for the reaction control engines and after-compartment equipment access.

The Block I fuel cells were located at the aft bulkhead in Sector 4, and their hydrogen and oxygen tanks were located in Sector 1. The three crew couches were constructed from hollow steel tubing and covered in a heavy, fireproof cloth known as Armalon. This was the same size as the oxidizer sump tank and held 8,708 pounds (3,950 kg) of fuel.

Diy. Sector 5 (70°) contained the SPS fuel sump tank.

Piston retraction compressed the probe and interface seals and actuated the 12 automatic ring latches which were located radially around the inner surface of the CSM docking ring. The Command Module provided a compartment for the crew and the mission's equipment, while the Service Module provided the spacecrafts power and propulsion. These combined hydrogen and oxygen to generate electrical power, along with some of the water used for drinking and other purposes. On the right were additional circuit breakers and a redundant audio control panel, along with the environmental control switches. The two negative pitch RCS engines located in the forward compartment were arranged vertically on Block I, and horizontally on Block II. Science. Since the spacecraft for the Skylab missions would not be occupied for most of the mission, there was lower demand on the power system, so one of the three fuel cells was deleted from these SMs. Flanking the sides of the main panel were sets of smaller control panels. Sector 3 (60°) contained the SPS oxidizer storage tank, which was the same shape as the sump tank but slightly smaller at 154.47 inches (3.924 m) high and 44 inches (1.1 m) in diameter, and held 11,284 pounds (5,118 kg) of oxidizer. [1] Therefore, design proceeded without a means of docking the Command Module to a Lunar Excursion Module (LEM). The separating force from the internal pressure in the tunnel area was then transmitted from the ring latches to the probe and drogue. Block I had slightly longer SPS fuel and oxidizer tanks which carried more propellant than Block II. The command module's inner structure was an aluminum "sandwich" consisting of a welded aluminum inner skin, a thermally bonded honeycomb core, and a thin aluminum "face sheet". [12], Media related to Apollo Command and Service Module at Wikimedia Commons, From Infogalactic: the planetary knowledge core, Major differences between Block I and Block II, CS1 maint: multiple names: authors list (, These included the crew couches, quick escape hatch, and metallic heat shield coating.

On the Apollo 6 unmanned Block I flights, the SM was painted white to match the Command Module's appearance, but on Apollo 1, Apollo 4, and all the Block II spacecraft, the SM walls were left unpainted except for the EPS and ECS radiators, which were white. An automatic extension latch attached to the probe cylinder body engaged and retained the probe center piston in the retracted position. Electrical equipment mass: 2,600 lb (1,200 kg), Service Propulsion (SPS) engine mass: 6,600 lb (3,000 kg), SPS engine propellants: 40,590 lb (18,410 kg), RCS thrust: two or four x 100 lbf (440 N), Spacecraft delta v: 9,200 ft/s (2,800 m/s), Electrical System: three 1.4 kW 30 V DC fuel cells, The Block II used a one-piece, quick-release, outward opening hatch instead of the two-piece. It was covered with a removable plug in the nose of the forward heat shield. The Service Module was an unpressurized cylindrical structure, measuring 24 feet 7 inches (7.5 m) long and 12 feet 10 inches (3.9 m) in diameter. This, plus other required design changes led to the decision to design two versions of the CSM: Block I was to be used for unmanned missions and a single manned Earth orbit flight (Apollo 1), while the more advanced Block II was designed for use with the Lunar Module. Medical experts have uncovered more evidence of sterilization practices on women held by ICE, New 3D moon models show it might hold up to 15,000 miles of frozen water, The best plugins for home music production. from Apollo Program Summary Report (April 1975) Command Module Interior.

CM was refitted with Block II improvements.

It held 7,058 pounds (3,201 kg) of fuel. It was 30 inches (76 cm) in diameter and weighed 80 pounds (36 kg). The exterior side was covered with a 0.5-inch (13 mm) of insulation and a layer of aluminum foil. Lunar modules were first used with Apollo 9. Sector 6 (60°) contained the SPS fuel storage tank, also the same size as the oxidizer storage tank. The steel honeycomb core and outer face sheets were then thermally bonded to the inner skin in a giant autoclave. The Command Module could be modified to carry extra astronauts as passengers by adding jump seat couches in the aft equipment bay.

In a temperature degraded condition, a single motor release operation was done manually in the Lunar Module by depressing the locking spool through an open hole in the probe heads, while release from the CSM was done by rotating a release handle at the back of the probe to rotate the motor torque shaft manually. It had an interior volume of 210 cubic feet (5.9 m3) and housed the main control panels, crew seats, guidance and navigation systems, food and equipment lockers, the waste management system, and the docking tunnel.

The omnidirectional antennas sufficed for ground communications during the Earth orbital missions, so the high gain S-band antenna on the SM was omitted from Apollo 1, Apollo 7, and the three Skylab flights. Dominating the forward section of the cabin was the crescent-shaped main display panel measuring nearly 7 feet (2.1 m) wide and 3 feet (0.91 m) tall. The Apollo Command Module could safely parachute to an ocean landing with at least two parachutes (as occurred on Apollo 15), the third parachute being a safety precaution. The sixteen-thruster arrangement provided rotation and translation control in all three spacecraft axes. Block II contained a shorter forward heat shield with a flat removable hatch, beneath a docking ring and probe mechanism which captured and held the LM. It also served as a retrorocket to perform the deorbit burn for Earth orbital Apollo flights.

The fairing segments were attached to the honeycomb panels and ring with conventional fasteners. Seeing Inside The Apollo Lunar Module. [5] When the Command and Lunar Modules separated for the last time just before re-entry, the probe and forward docking ring were pyrotechnically separated, leaving all docking equipment attached to the lunar module. The aft heat shield was nearly identical to the central, except no alluminized film layer was applied. Storage tanks were carried for water and oxygen. In the event of an abort during launch from Earth, the same system would have explosively jettisoned the docking ring and probe from the CM as it separated from the boost protective cover. The exhaust nozzle engine bell measured 152.82 inches (3.882 m) long and 98.48 inches (2.501 m) wide at the base.

December 16, 2013.

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